基于移动热边界的动涡旋盘温度场有限元分析

Finite Element Analysis Based on Moving Thermal Boundary for Orbiting Scroll Wrap's Temperature Distribution

为了得到更符合空气涡旋压缩机实际运行工况的涡旋盘温度场,依据压缩过程中涡旋盘上热边界的变化规律,计算了周期变化过程中各压缩腔的温度及对流换热系数。将涡旋盘受热面分割为多个子面,通过对这些子面以多载荷步的形式施加周期变化的对流换热载荷,实现涡旋盘动态温度场的仿真求解。研究结果表明:涡旋盘上的温度是由中心向外围逐渐扩散的,涡旋盘上的温度变化趋势表现为先快速升温,后缓慢升高,最后趋于稳定;并且当涡旋盘上的温度趋于稳定后,涡旋齿高方向温差为先逐渐减小为0,后反向增大。

In order to obtain a scroll temperature field which is more in accordance with the actual operating conditions of air scroll compressor,according to the variation law of thermal boundary on the scroll during a compression process,we calculate the temperature and convective heat transfer coefficient of each compression chamber during cyclic variation.We divide the heated surface of the scroll into many sub-surfaces.We apply a cyclically varying convective heat transfer load to these sub-surfaces in the form of multi-load steps,and realize a simulation of the dynamic temperature field of scroll.The results show that the temperature on the scroll gradually diffuses from center to periphery;the trend of scroll's temperature change is that the temperature rises rapidly first,then slowly,and finally tends to be stable;when the temperature of orbiting scroll gradually stabilizes,the temperature difference in the direction of scroll wrap is gradually reduced to zero first,and then increases in the reverse direction.